EP1946913A1 - Procédé et appareil de fabrication d'un élément de longeron d'aile - Google Patents

Procédé et appareil de fabrication d'un élément de longeron d'aile Download PDF

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Publication number
EP1946913A1
EP1946913A1 EP07100884A EP07100884A EP1946913A1 EP 1946913 A1 EP1946913 A1 EP 1946913A1 EP 07100884 A EP07100884 A EP 07100884A EP 07100884 A EP07100884 A EP 07100884A EP 1946913 A1 EP1946913 A1 EP 1946913A1
Authority
EP
European Patent Office
Prior art keywords
forming
blank
protrusion
forming surface
flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07100884A
Other languages
German (de)
English (en)
Other versions
EP1946913B1 (fr
Inventor
Max Krogager
Jan Vaara
Mikael Petersson
Björn Weidmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Saab AB
Original Assignee
Saab AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Saab AB filed Critical Saab AB
Priority to AT07100884T priority Critical patent/ATE501835T1/de
Priority to ES07100884T priority patent/ES2359090T3/es
Priority to DE602007013173T priority patent/DE602007013173D1/de
Priority to EP07100884A priority patent/EP1946913B1/fr
Priority to US12/010,180 priority patent/US20090025865A1/en
Publication of EP1946913A1 publication Critical patent/EP1946913A1/fr
Application granted granted Critical
Publication of EP1946913B1 publication Critical patent/EP1946913B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/386—Automated tape laying [ATL]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0003—Producing profiled members, e.g. beams
    • B29D99/0007—Producing profiled members, e.g. beams having a variable cross-section
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B29L2031/3085—Wings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
    • Y10T156/1007—Running or continuous length work

Definitions

  • a beam made of reinforced resin composite wherein the fibres must follow the curvature of the beam.
  • a common method is to, as a first step, apply "prepreg" material (layers of fibre material previously impregnated with resin, such as thermosetting resin) onto a web forming tool surface and thereafter forming the flanges about flange forming surfaces of the tool. This often involves extra work efforts and the blank material has a tendency to be crinkled.
  • ATL-apparatus automated tape laying
  • plies of prepreg material onto each other providing a rectangular blank, which rectangular blank can be formed into a profile element, such as a C-beam, L-beam etc, without the need of removing material from the blank after curing.
  • a wing of an aircraft comprises one or more wing spars embodied within the wing shell.
  • an aircraft such as airliner, comprises two or four power plants located below and ahead of the wing, each power plant is connected to the wing via an engine support.
  • the prior art wing spars are provided with cavities, each embodying the engine support of the respective power plant such that the power plant can be arranged as near as possibly to the wing chord. These cavities are achieved by milling of composite material of the wing spar's lower flange. It is also desirable to have the power plants located as near as possible the line of the wing chord due to the maj or drag forces created by the power plants during take-off.
  • the profile element is formed by application of a blank of prepreg material over a male tool portion having forming surfaces, thereby forming the flange and web portions. Thereafter the blank is cured. The curing can take place within a vacuum bag and by means of heat. The above-mentioned mill of is thereafter performed for providing the cavities making it possibly to mount the power plants nearer the wing chord.
  • US 6 355 133 discloses a method of forming a composite article that comprises a plastics materials reinforced with fibres.
  • a forming step is carried out on the blank, whereby its planar surface is formed into a right angle, whilst still conforming to the form tool an operation carried out whilst applying increased heating to the component.
  • the article is constrained against movement in a direction perpendicular to the plane of the main direction of layers and forces are applied to the article in the plain thereof in a direction substantially perpendicular to the main direction of the fibres.
  • the article is thereby urged into conformity with the contoured surface of the tool while substantially maintaining the continuity of the fibres.
  • the object of the present invention is to overcome the drawbacks of known methods and apparatuses for manufacture of air craft wing spars, having at least a recess for accommodating support element.
  • a wing spar element can be achieved adapted for partly embodying at least one power plant support having its upper part nearer the wing chord making it possibly to fasten the power plant to the underside of wing such that sufficient ground clearance is achieved, keeping the landing gear as short as possible, during taxiing and take-off, without the need of milling of composite material for providing a recess in the wing spar and without the costly manufacture step of applying reinforcement material to the wing spar within the area of the recess, which also would involve higher weight to the aircraft.
  • other elements such as weapon system supports etc., can be located within such a recess.
  • the step of forming the blank also includes the forming of the blank into a second flange portion with at least one third protrusion formed to extend across the second flange portion and to protrude inward from the inner surface of the second flange portion, wherein this third protrusion merges into the first protrusion.
  • a C-beam like wing spar can be achieved having the recess on the underside of the wing spar.
  • a recess is achieved in the beam for accommodating the power plant support, without milling of material.
  • An ATL-apparatas can be used in an automated production line for applying plies of prepreg material for making the blank, wherein the blank is used for the manufacture of the C-beam having a recess according to the present invention for accommodating for example a power plant support.
  • the step of curing the blank includes the process of heating the blank applied onto the forming tool.
  • the curing of the blank is performed by sealing the blank in a vacuum bag; evacuating air from the vacuum bag; and heating the blank by means of a heating means.
  • the beam can be finished in a short time and in a labour saving manner, directly in the forming tool.
  • the blank comprises plies of prepreg-material including reinforcement fibres.
  • an apparatus comprising a forming tool that can be used for forming of for example an L-beam or C-beam profile element having a recess for accommodating a support element, for example a power plant support, without the need of cutting the profile element for creating a recess.
  • the forming tool further comprises a second flange forming surface comprising a curved inward forming surface for forming of a curved inward protrusion of a second flange portion.
  • the web forming and flange forming surfaces have a curvature along the elongation of the forming tool.
  • curved C-beams can be formed having a recess for accommodating a support element.
  • the flange forming surface comprises two curved inward forming surfaces for making two recesses, each inward forming surface merging with a respective outward forming surface.
  • profile element can be cost-effective manufactured, which profile element can be used for an aircraft wing spar, wherein two support elements, such as power plant supports, can be mounted near the wing chord.
  • FIG. 1a illustrates an aircraft 1 without any recesses in its wing spar 103, thereby not accommodating power plant support elements 4.
  • the aircraft 1 is located on the ground surface 5 before take-off.
  • the aircraft's wing 7 comprises the wing spar 103 embodied within the wing shell 9.
  • the aircraft 1 comprises two power plants 11 (only one is shown) located below the wing 7, each power plant 11 is connected to the wing 7 via the power plant support element 4.
  • the distance between ground surface 5 and the power plant 11 is marked with d'.
  • prior art wing spars are provided with cavities or recesses, achieved by machining the wingspar (by milling of composite material of the wing spar's lower flange or web at the location of the cavities).
  • the support element of the respective power plant is thus arranged as near as possibly to the wing chord.
  • FIG. 1b illustrates a twin engine aircraft 1 having a wing spar 3 comprising two recesses 15 (see FIG. 2a ) accommodating the power plant support elements 4 for creating a further distance between the ground surface 5 and the power plants 11.
  • the distance is marked with d" and is greater than the distance d' in FIG. 1a .
  • This distance d" is desirable for solving the problem of, keeping the landing gear 39 as short as possible, creating a sufficient ground clearance between the power plant 11 and the ground surface 5 during taxiing and take-off.
  • FIG. 2a illustrates a perspective view of the C-beam, or wing spar 3 shown in FIG. 1b , comprising a recess 15 for accommodating a support element 4 (see FIG. 2b ) nearer the wing chord.
  • the wing spar 3 is manufactured by applying a blank 28 of resin composite material about a first flange forming surface 29 and a web forming surface 31 of a forming tool 33 (see FIG. 4a and 4b ).
  • the blank 28 is made by an ATL-apparatus (automatic tape laying machine) (not shown) in a cost effective manner.
  • the ATL-apparatus can be reprogrammed for different types of blanks 28 earmarked for a certain wing spar.
  • Prepreg tapes (not shown) including fibres (not shown) of carbon extending in the longitudinal direction of the pregreg tape are applied by the ATL-apparatus perpendicular and diagonally to and also along the longitudinal direction of the blank 28.
  • the blank 28 is formed into the web portion 23 with a first ridge (outwardly protrusion 21) formed to extend across the web portion 23 and to protrude outward from the outer surface 35 (se FIG. 5 ) of the web portion 23.
  • the first flange portion 17 is formed comprising a second ridge (inwardly protrusion 19) being formed to extend across the first flange portion 17 and to protrude inward from the inner surface 37 of the first flange portion 17, wherein this second ridge merges into the first ridge and constitutes said recess 15 (indicated with reference 15 in FIG. 5 ) for accommodating the power plant support element 4 shown in FIG. 2b .
  • the second flange portion 27 (see FIG. 2b ) is formed with a third ridge (inwardly protrusion 25) formed to extend across the second flange portion 27 and to protrude inward from the inner surface of the second flange portion 27, wherein this third ridge merges into the first ridge.
  • a C-beam wing spar comprising the recess 15 for accommodating a support element onto the underside of the wing spar 3, without affecting the weight or strength of the wing spar.
  • a recess is achieved in the C-beam for accommodating the power plant support, without milling of material.
  • An ATL-apparatus can be used in an automated production line applying plies of prepreg material making the blank 28.
  • the cost-effective made blank 28 can be used for the manufacture of the C-beam having a recess 15 according to the invention for accommodating for example a power plant support 4.
  • the curing of the blank 28 is performed by sealing the blank 28 in a vacuum bag (not shown), evacuating air from the vacuum bag and heating the blank 28 by means of a heating means (not shown). Thereby the C-beam can be finished in a short time and in a labour saving manner directly in the forming tool.
  • the heating is controlled by a control unit (not shown) for controllable curing.
  • a wing spar element 3 is achieved, adapted for partly embodying at least one power plant support 4 having the support's upper part nearer the wing chord WC (see FIG. 1b ) making it possibly to providing the power plant 11 to the underside of the wing 7 such that sufficient ground clearance is achieved, keeping the landing gear 39 (see FIG. 1b ) as short as possible, during taxiing and take-off, without the need of milling of composite material for providing a recess in the wing spar 3 and without the costly manufacture step of applying reinforcement material to the wing spar within the area of the recess, which also would involve higher weight to the aircraft.
  • FIG. 2b illustrates a cross section corresponding with plane P in FIG. 2a .
  • the cross section is taken through the portion of the wing spar 3, wherein a part of the first flange 17 is curved inward, forming the recess 15 (first inwardly protrusion 19). Dashed and dotted line shows a support element 4 accommodated in the recess 19 partly.
  • an opposite inwardly protrusion 25 is formed in the second flange 27, which protrusion 25 together with the outwardly protrusion 21 compensate the first inwardly protrusion 19.
  • the outwardly protrusion 21 merges with the first 19 and second 25 inwardly protrusions of the web portion, such that a geometric compensation is achieved.
  • the strength of the wing spar is maintained since no fibres have to be cut of and the fibres follow the structure of the wing spar 3 smoothly.
  • FIG. 3 illustrates partly a cross section of a wing 7 comprising two wing spars 3 having recesses.
  • Each wing spar 3 i.e. elongated beam profile element
  • the wing spar 3 also comprises a second flange portion 27 located opposite the first flange portion 17.
  • Each of the first flange portions 17 comprises the recess 15 (first inwardly protrusion 19) provided for accommodating a support element, such as a power plant support 4.
  • FIG. 4a illustrates a forming tool's male forming tool 33 (only partly illustrated) of an apparatus for forming of the C-beam in FIG. 2a .
  • the blank (not shown) is to be placed onto the male forming part tool 33.
  • the blank comprises plies of prepreg-material including fibres having reinforcement fibres.
  • the apparatus comprises the web forming surface 31 and the first 29 and second (not shown) flange forming surface provided on the male forming tool 33 for forming the blank into the elongated wing spar profile element 3.
  • the male forming tool's 33 first flange forming surface 29 is provided with a curved inward forming surface 41 for forming of the curved inward ridge making the recess 15 (first inwardly protrusion 19) of the first flange portion 17 (see FIG. 2b ).
  • the web forming surface 31 is provided with a curved outward forming surface 43 for forming of the curved outward ridge (protrusion 21) of the web portion 23 (see FIG. 2b ).
  • the magnitude of the curved inward forming surface's 41 area corresponds with the magnitude of the curved outward forming surface's 43 area, such that a geometric compensation is achieved for the blank 28, wherein the blank 28 will not wrinkle.
  • the area of the inward protrusion surface must be the same as the area of the outward protrusion.
  • this relation can be varied since curved elongated wing spars, due to the curvature, require a sometimes not equal relationship.
  • FIG. 4b illustrates a cross section A-A in FIG. 4a .
  • the forming tool's 33 curved outward forming surface 43 (only half of which is shown) merges into the inward forming surfaces 41 of the first and second flange forming portions 29, 30.
  • the apparatus in FIG. 4a-4b can be used for forming of an L-shaped wing spar (see FIG. 5 ) as well, having a recess for accommodating a support element. However with different curvature for the recess 15 (inwardly protrusion 19) and for the compensating outwardly protrusion 21, each of which having a sharp bent.
  • the L-shaped wing spar shown in FIG. 5 comprises a first elongated flange portion 17 and a web portion 23 joining each other.
  • the first ridge (outwardly protrusion 21) formed to extend across the web portion 23 and to protrude outward from the outer surface 35 of the web portion 23.
  • a second ridge (inwardly protrusion 19) being formed to extend across the first flange portion 17 and to protrude inward from the inner surface 37 of the first flange portion 17, wherein this second ridge merges into the first ridge and constitutes said recess 15 for accommodating the support element under the wing.
  • the profile element's web portion can be formed with an inward protrusion and the flanges with outward protrusions.
  • the outward protrusions compensating the inward protrusion, so that no material has to be cut of.
  • the inward protrusion of the web portion is directed towards the wing's underside.
  • the magnitude (or extension) of the curved inward forming surface's area corresponds with the magnitude (extension) of the curved outward forming surface's area, such that a geometric compensation is achieved.
  • the area of the protrusion surface inward must be the same as the area of the protrusion outward.
  • this relation can be varied, since curved elongated wing spars, due to the curvature, sometimes require a not equal relationship between said areas.
  • the forming tool can be slightly bent for forming a profile element having a curvature.
  • the composite plastic can be thermo setting plastic, epoxi resins, thermoplastics, polyester resins, fibreglass reinforced plastics etc.
  • the forming and curing process of the blank can also use a female forming tool co-operating with the male forming tool.
  • the heating means can be in the form of electrical heater element, water radiators, heating resistor elements, heated air etc.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Robotics (AREA)
  • Moulding By Coating Moulds (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Extrusion Moulding Of Plastics Or The Like (AREA)
EP07100884A 2007-01-22 2007-01-22 Procédé et appareil de fabrication d'un élément de longeron d'aile Active EP1946913B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
AT07100884T ATE501835T1 (de) 2007-01-22 2007-01-22 Verfahren und vorrichtung zur herstellung eines tragflächenholmprofilelements
ES07100884T ES2359090T3 (es) 2007-01-22 2007-01-22 Procedimiento y aparato para la fabricación de un elemento de perfil de larguero de ala.
DE602007013173T DE602007013173D1 (de) 2007-01-22 2007-01-22 Verfahren und Vorrichtung zur Herstellung eines Tragflächenholmprofilelements
EP07100884A EP1946913B1 (fr) 2007-01-22 2007-01-22 Procédé et appareil de fabrication d'un élément de longeron d'aile
US12/010,180 US20090025865A1 (en) 2007-01-22 2008-01-22 Method and apparatus for manufacturing of a wing spar profile element

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07100884A EP1946913B1 (fr) 2007-01-22 2007-01-22 Procédé et appareil de fabrication d'un élément de longeron d'aile

Publications (2)

Publication Number Publication Date
EP1946913A1 true EP1946913A1 (fr) 2008-07-23
EP1946913B1 EP1946913B1 (fr) 2011-03-16

Family

ID=38169656

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07100884A Active EP1946913B1 (fr) 2007-01-22 2007-01-22 Procédé et appareil de fabrication d'un élément de longeron d'aile

Country Status (5)

Country Link
US (1) US20090025865A1 (fr)
EP (1) EP1946913B1 (fr)
AT (1) ATE501835T1 (fr)
DE (1) DE602007013173D1 (fr)
ES (1) ES2359090T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019178072A1 (fr) * 2018-03-12 2019-09-19 Cytec Industries Inc. Fabrication de structures composites tridimensionnelles

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Publication number Priority date Publication date Assignee Title
GB0906157D0 (en) * 2009-04-09 2009-05-20 Airbus Uk Ltd Improved wing structure
US8763153B2 (en) * 2011-05-10 2014-06-24 Microsoft Corporation Presenting messages associated with locations
US10105940B2 (en) * 2016-04-18 2018-10-23 The Boeing Company Formation of composite laminates having one or more divergent flanges
ES2800182T3 (es) * 2017-07-13 2020-12-28 Airbus Operations Sl Disposición estructural de caja para una aeronave y procedimiento de fabricación de la misma
US10682821B2 (en) * 2018-05-01 2020-06-16 Divergent Technologies, Inc. Flexible tooling system and method for manufacturing of composite structures

Citations (5)

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Publication number Priority date Publication date Assignee Title
US4475976A (en) * 1983-12-23 1984-10-09 The Boeing Company Method and apparatus for forming composite material articles
US6114012A (en) * 1997-03-19 2000-09-05 Fuji Jukogyo Kabushiki Kaisha Rib of composite material and method of forming the same
US6355133B1 (en) 1998-12-22 2002-03-12 Bae Systems Plc Forming reinforcing components
US20050183818A1 (en) * 2004-02-25 2005-08-25 Zenkner Grant C. Apparatus and methods for processing composite components using an elastomeric caul
EP1731291A1 (fr) * 2005-06-08 2006-12-13 Saab Ab Appareil de positionnement automatique de bandes et procédé utilisant cet appareil

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US4351688A (en) * 1979-12-10 1982-09-28 General Dynamics Corporation Composite tape laying machine
US4451528A (en) * 1981-03-30 1984-05-29 Ni Industries, Inc. Composite fiber reinforced member and method
US5242523A (en) * 1992-05-14 1993-09-07 The Boeing Company Caul and method for bonding and curing intricate composite structures
US5753164A (en) * 1995-08-30 1998-05-19 The Budd Company Automated thermoset molding method
ES2205961B2 (es) * 2001-02-13 2005-03-01 Eads Construcciones Aeronauticas, S.A. Procedimiento de fabricacion de elementos de material compuesto mediante la tecnoclogia del coencolado.
US6758439B2 (en) * 2002-10-22 2004-07-06 The Boeing Company Apparatuses and methods for attaching engine nacelles to aircraft
JP2006312260A (ja) * 2005-05-09 2006-11-16 Fuji Heavy Ind Ltd プリプレグの折曲成形装置及びその折曲成形方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4475976A (en) * 1983-12-23 1984-10-09 The Boeing Company Method and apparatus for forming composite material articles
US6114012A (en) * 1997-03-19 2000-09-05 Fuji Jukogyo Kabushiki Kaisha Rib of composite material and method of forming the same
US6355133B1 (en) 1998-12-22 2002-03-12 Bae Systems Plc Forming reinforcing components
US20050183818A1 (en) * 2004-02-25 2005-08-25 Zenkner Grant C. Apparatus and methods for processing composite components using an elastomeric caul
EP1731291A1 (fr) * 2005-06-08 2006-12-13 Saab Ab Appareil de positionnement automatique de bandes et procédé utilisant cet appareil

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019178072A1 (fr) * 2018-03-12 2019-09-19 Cytec Industries Inc. Fabrication de structures composites tridimensionnelles
US11654647B2 (en) 2018-03-12 2023-05-23 Cytec Industries Inc. Fabrication of three-dimensional composite structures

Also Published As

Publication number Publication date
EP1946913B1 (fr) 2011-03-16
ATE501835T1 (de) 2011-04-15
US20090025865A1 (en) 2009-01-29
ES2359090T3 (es) 2011-05-18
DE602007013173D1 (de) 2011-04-28

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